Search Results for “aerodynamic experiment” – Collected book of scientific-technical articles

9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

manager — Tue, 03 Oct 2023 11:48:27 +0000

9. Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Sirenko V. M., Zhivotov O. Yu.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 63-70

DOI: https://doi.org/10.33136/stma2019.02.063

Language: Russian

Annotation: A promising experimental bench – a shock wind tunnel was put into operation at Yuzhnoye SDO. The shock wind tunnel is designed to simulate the incident flow during rocket flight at high supersonic and hypersonic velocities. To solve actual design problems facing Yuzhnoye SDO, it was necessary to expand the range of velocities under investigation in a shock wind tunnel by low supersonic Mach numbers (Mа=1.5; 2; 3). As a result of this work, a modernized configuration of the shock wind tunnel was developed, which allows simulating flow parameters at low supersonic velocities. The results of aerodynamic experiment performed in the modernized shock wind tunnel, which are close to full scale ones, can be obtained using as much data on peculiarities of supersonic flow formation in it as possible. Therefore, the study of the distribution of Mach numbers profiles in the working section of the modernized shock wind tunnel at low and high supersonic velocity was chosen as the main line of research. The results of the research presented in the article are based on the use of numerical simulation methods, as well as data obtained experimentally. As a result of gasdynamic simulation of a supersonic flow conducted for the nozzle Mа=4 and the nozzle Mа=2, the calculated and experimental data on the distribution pattern and field values of Mach numbers in the working section of the tunnel were obtained. A comparative analysis was carried out. The boundaries of the region of equal velocities, within which the condition of quasistatic supersonic flow is satisfied, and the lifetime of the operating mode for the selected nozzle type were determined. At the flow from the nozzle Mа=2, a peculiarity was revealed in the distribution pattern of Mach numbers fields associated with the appearance of “blocking” effect of the supersonic flow. The methods for eliminating the effect of flow “blocking” at low supersonic velocities are proposed.

Key words: incident flow modeling, velocity fields in the wind tunnel working section, aerodynamic experiment

Bibliography:

1. Zvegintsev V. I. Gasodynamicheskie ustanovki kratkovremennogo deistviya. V dvuh chastyakh. Ch. 1. Ustanovki dlya nauchnykh issledovaniy. Novosibirsk, 2014. 551 s.

2. Computerno-vymiryuvalni tekhnologii kontrolu ta upravlinnya raketno-kosmichnoi techniki / monogr. pid zagal. red. prof. V. P. Malaichuka. Dnipro, 2018. 344 s.

3. «Sirius-18». Systema izmereniya i upravleniya impulsnoi aerodynamicheskoi truboi. Rukovodstvo po ekspluatatsii. ELVA4.044.901 RE. 2018. 45 s.

4. Abramovich G.N. Prikladnaya gazovaya dynamika. M., 1978. 888 s.

5. Raschet vnutrennego davlenia v otsekakh RN. YSF YZH UMN 041 01. Rukovodstvo operatora. 2016. 138 s.

6. Issledovania characteristic hyperzvukovoi aerodynamicheskoi truby AT-303. Ch. 1. Polya skorostey / A. M. Kharitonov at al. Teplophysika i aeromekhanika. 2006. T. 13, № 1. S. 1–17.

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17.1.2020 Acoustic problems of rocket launch

Вацлав Самусевич — Wed, 13 Sep 2023 11:36:44 +0000

17. Acoustic problems of rocket launch

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Hrinchenko V. T.

Organization:

Institute of Hydromechanics of National Academy of Sciences of Ukraine, Kyiv, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 155-159

DOI: https://doi.org/10.33136/stma2020.01.155

Language: Russian

Annotation: Due to an increase of power of rocket engines, the high intensity sound field generated by the exhaust jets have become an important factor, which determines the success rate of a rocket launch. Ensuring a successful launch of a rocket system became harder due to new engineering problems. Identification and definition of acoustic sources structure within a complex supersonic jet, being a one of the most important scientific problems, which have to be solved to find the ways to control accoustic radiation. A three components of acoustic sources can be defined here – broadband signals from large and small components of of turbulent jet and tonal signals which usually being overlooked during the estimation of overall sound pressure level. The paper considers various aspects of acoustics of the launch of rocket systems, which includes characteristics of acoustic sources in supersonic jets, possibilities and physical limitation factors, under which it is possible to control the sound radiation. Among the possible ways to control the process of sound generation by a jet, a method of water injection in a jet is being studied. While saving the general thrust of the engine this method can not greatly reduce the sound radiation by a jet. It is recommended to use big amounts of water-air mix to protect the launch pad from damage. Significant progress on the topic of understanding the process of sound generation by supersonic jets can be achieved via mathematical modeling of sound radiation. The latest achievements of mathematical modeling of sound generation by supersonic jets being presented.

Key words: Acoustics of rocket launch, acoustic efficiency of a jet, semi-empirical models of of jet acoustics, numeric-computational methods in aeroacoustics, control of jet-generated acoustic levels

Bibliography:

1. Lighthill M. J. On Sound Generated Aerodynamically: I. General Theory. Proc. Roy. Soc. London Ser. A, 211. 1952. Р. 564–581. https://doi.org/10.1098/rspa.1952.0060

2. Tam C. K. W. Jet noise. Theoretical Computftional Fluid Dynamics. 1998. No 10. Р. 393–405. https://doi.org/10.1007/s001620050072

3. Lubert C. P. Sixty years of launch vehicle acoustics. Proc.Mtgs.Acoust. Vol. 31. 2017. https://doi.org/10.1121/2.0000704

4. Ask the Astronaut: What does launch feel like? URL: https://www.airspacemag. com/ask-astronaut/ask-astronaut-what-does-launch-feel-what-thoughts-and-emotions-run-through-your-mind-180959920/

5. Tim P. Ask an Astronaut: My Guide to Life in Space. 2018. 272 p.

6. Saucer B. What’s the Deal with Rocket Vibration? MIT Technology Review. July 15, 2009. URL: https://www.technology-review.com/s/414364https:/whats-the-deal-with-rocket-vibrations/

7. Ross D. Mechanics of Underwater noise. 1976. 266 p.

8. Varnier J. Experimental study and simulation of rocket engine free jet noise. AIAA J. 2001. Vol. 39, Nо 10. P. 1851–1859. https://doi.org/10.2514/2.1199

9. Eldred K. M. Acoustic loads generated by the propulsion system. NASA SP-8072, 1971. 49 p.

10. Balakrishnan P., Srinivason K. Impinging get noise reduction using non-circular jets. Applied Acoustics. 2019. Vol. 143. Р. 19-30. https://doi.org/10.1016/j.apacoust.2018.08.016

11. Tsutsumi S. Acoustic generation mechanism of a supersonic jet impinging on deflectors / S. Tsutsumi, R. Takaki, Y. Nakanishi, K. Okamoto, S. Teramoto 52th AIAA Aerospace Sci. Meet. AIAA Pap. 2014-0882. 2014. 12 p. https://doi.org/10.2514/6.2014-0882

12. Ahuja K. K., Manes J. P., Massey K. C., Calloway A. B. An Evaluation of various concepts of Reducing Supersonic Jet Noise, AIAA-90-3982. AIAA 13th Aeroacoustic Conference, 1990. Р. 1-21. https://doi.org/10.2514/6.1990-3982

13. Krathapalli A., Lenkatakrishnan L., Elovarsan R., Laurenco L. Supersonic Jet Noise Suppression by Water Injection. AIAA 2000-2025. 6th AIAA/CEAS Aeroacoustic Conference, 2000. Р. 1-25.

14. Moratilla-Vega M. A., Lackhole K., Janicka J., Xia H., Page C. J. Jet Noise Analysis using an Efficient LES/ High-Order Acoustic Coupling Method. Computer and Fluid. 2020. https://doi.org/10.1016/j.compfluid.2020.104438

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10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

Вацлав Самусевич — Thu, 07 Sep 2023 11:29:45 +0000

10. Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Nikitenko K. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 83-93

DOI: https://doi.org/10.33136/stma2018.02.083

Language: Russian

Annotation: At Yuzhnoye State Design Office, the Cyclone-4 launch vehicle 3rd stage engine has been developed and is under testing. For adjustment of the engine and test bench systems, in the first firing tests the radiation-cooled nozzle extension was replaced with a steel water-cooled one. It was planned to start the engine with water-cooled nozzle extension without vacuumizing and without gad dynamic pipe, which conditioned operation with flow separation at the output edge of water-cooled nozzle extension. Therefore, the calculation of flow in the nozzle with water-cooled extension, flow separation place, and thermal load on watercooled nozzle extension during operation in ground conditions is an important task. Selection of turbulent flow model has a noticeable impact on prediction of flow characteristics. The gas dynamic analysis of the nozzle with water-cooled extension showed the importance of using the turbulent flow model k-ω SST for the flows with internal separation of boundary layer and with flow separation at nozzle section. The use the flow model k-ω SST for calculation of nozzle with flow separation or with internal transitional layer allows adequately describing the flow pattern, though, as the comparison with experimental data showed, this model predicts later flow separation from the wall than that obtained in the tests. The calculation allows obtaining a temperature profile of the wall and providing the recommendations for selection of pressure measurement place in the nozzle extension for the purpose of reducing sensors indication error. With consideration for the special nature of the nozzle extension wall temperature field, the cooling mode was selected. The tests of RD861K engine nozzle with water-cooled extension allow speaking about its successful use as a required element for testing engine start and operation in ground conditions without additional test bench equipment.

Key words: turbulent flow, flow separation, cooling, technological extension

Bibliography:

1. Massiet P., Rocheque E. Experimental Investigation of Exhaust Diffusors for Rocket Engines. Investigation of Liquid Rocket Engines. М., 1964. P. 96-109.

2. Mezhevov A. V., Skoromnov V. I., Kozlov A. V. et al. Introduction of Radiation Cooling Nozzle Head of Made of Carbon-Carbon Composite Material on DM-SL Upper Stage 11D58M Main Engine. News of Samara Aerospace University. No. 2 (10). 2006. P. 260-264.

3. Fluent. Software Package, Ver. 6.2.16, Fluent Inc., Lebanon, NH, 2004.

4. Wilcox D. C. Turbulence Modeling for CFD. DCW Industries, Inc. La Canada, California, 1998. 460 р.

5. Andersen D., Tannehill J., Platcher R. Computational Hydromechanics and Heat Exchange: in 2 volumes М., 1990. 384 p.

6. Rodriguez C. G., Culter, A. D. Numerical Analysis of the SCHOLAR Supersonic Combustor, NASA-CR-2003-212689. 2003. 36 р.

7. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952

8. Spalart P., Allmaras S. A one-equation turbulence model for aerodynamic flows: Technical Report. American Institute of Aero-nautics and Astronautics. AIAA-92-0439. 1992. Р. 5-21. https://doi.org/10.2514/6.1992-439

9. Launder B. E., Spalding D. B. Lectures in Mathematical Models of Turbulence. London, 1972. Р. 157-162.

10. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952

11. Ten-See Wang. Multidimensional Unstructured Grid Liquid Rocket-Engine Nozzle Performance and Heat Transfer Analysis. Journal of Propulsion and Power. Vol. 22. No. 1. 2006. 21 р. https://doi.org/10.2514/1.14699

12. Hyun Ko, Woong-Sup Yoon. Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle. Journal of Propulsion and Power. Vol. 18, No. 3. 2002. Р. 585-591. https://doi.org/10.2514/2.5972

13. Wilson E. A., Adler D., Bar-Yoseph P. Thrust-Vectoring Nozzle Performance Mode-ling. Journal of Propulsion and Power. Vol. 19, No. 1. 2003. Р. 39-47. https://doi.org/10.2514/2.6100

14. Gross A., Weiland C. Numerical Simulation of Hot Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 5. 2004. Р. 879-891. https://doi.org/10.2514/1.5001

15. Gross A., Weiland C. Numerical Simulation of Separated Cold Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 3. 2004. Р. 509-519. https://doi.org/10.2514/1.2714

16. Deck S., Guillen P. Numerical Simulation of Side Loads in an Ideal Truncated Nozzle. Journal of Propulsion and Power. Vol. 18, No. 2. 2002. Р. 261-269. https://doi.org/10.2514/2.5965

17. Östlund J., Damgaard T., Frey M. Side-Load Phenomena in Highly Overexpanded Rocket Nozzle. Journal of Propulsion and Power. Vol. 20, No. 4. 2004. Р. 695-704. https://doi.org/10.2514/1.3059

18. Goldberg U. C. Separated Flow Treatment with a New Turbulence Model. AIAA Journal. Vol. 24, No. 10. 1986. Р. 1711-1713. https://doi.org/10.2514/3.9509

19. Golovin V.S., Kolchugin B.A., Labuntsov D.A. Experimental Investigation of Heat Exchange and Critical Heat Loads at Water Boiling in Free Motion Conditions. 1963. Vol. 6, No 2. p. 3-7.

20. Mikheyev М. А., Mikheyeva I. M. Heat-Transfer Principles. 2nd edition stereotyped. М., 1977. 343 p.

21. Kutateladze S. S., Leontyev A. I. Heat-Mass Exchange and Friction in Turbulent Boundary Layer. М., 1972. 341 p.

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19.2.2017 Experience in Development of Pneumatic System for Aerodynamic Payload Fairing Separation

Виктория Лемех — Wed, 09 Aug 2023 12:23:07 +0000

19. Experience in Development of Pneumatic System for Aerodynamic Payload Fairing Separation

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Kabakova Zh. V., Kuda S. А., Logvinenko A. I., Khomyak V. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 107-111

Language: Russian

Annotation: The paper presents the generalized experience of designing and development testing of the pneumatic system for nose aerodynamic fairing halves jettisoning. The algorithm of its parameters calculation is given. The satisfactory convergence of the pneumatic system parameters calculation results with the experimental data from the ground and flight tests is shown.

Key words:

Bibliography:

1. Basis of Calculation of Gas Parameters in Pneumatic Systems Operation: Teacher Edition of Yuzhnoye SDO. 21.7217.123 ОТ. 1988.

2. Cyclone-4 SLS. Analysis of Experimental Data on PLF Doors Jettison Pneumatic System: Technical Report / Yuzhnoye SDO. Cyclone-4 21.17689.213 ОТ. 2014.

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Сollected book of scientific-technical articles

manager — Thu, 04 May 2023 07:56:30 +0000

The collection of scientific and technical articles Space Technology. Missile Armaments is a specialized professional publication that publishes new results of theoretical and experimental research and development in the field of aviation and space rocket technology.

The subject area of the Collection corresponds to the Mechanical Engineering and Machine-Building cluster (G8 Materials Science, G9 Applied Mechanics, G10 Metallurgy, G11 Industrial Engineering, and G12 Aviation, Rocket, and Space Technology).

The scope of the Collection covers the development and operation of state-of-the-art military missile and space launch systems, spacecraft, and satellite systems, as well as their components, including:

Design and development of missile and ground-based systems.
Design and development of components of space launch vehicles and combat missiles (liquid-propellant and solid-propellant rocket engines, propulsion systems, control systems, separation systems, payload equipment, etc.)
Design and development of components for ground-based systems (facilities, fueling systems, prelaunch processing systems, etc.)
Design and development of spacecraft and their components.
Problems of aerodynamics, heat and mass transfer, flight theory, loading, and structural strength.
Problems of efficiency, reliability, safety, and economic feasibility of space launch systems.
Other aspects that are directly related to the development and operation of space launch systems.
Other topics corresponding to the Mechanical Engineering and Manufacturing

The target audience is scientists, postgraduate students, and specialists whose scientific interests include achievements in aviation, rocket, and space technology (G12) and other specialties within the Mechanical Engineering and Machine-Building cluster (G8, G9, G10, and G11).

The Collection is included in the List of Scientific Professional Publications of Ukraine (category B) in accordance with Order No. 928 of the Ministry of Education and Science, dated June 11, 2026 (Appendix 5).

The Collection is registered in the unified open scientific identification system ROR (Research Organization Registry).

The collection of scientific and technical articles Space Technology. Missile Armaments has been published since April 1979. It is currently published in printed (ISSN 2617-5525) and identical in content, full-text electronic forms (e-ISSN 2617 5533).

Publications in the Collection are provided free of charge for both authors and users (Diamond Open Access). No fees are charged to authors for the processing, peer review, or publication of the articles in the Collection or on its website.

About the collected articles

ISSN 2617-5525 (Print); e-ISSN 2617-5533 (Online)

ISSN 2617-5525 (Print);
e-ISSN 2617-5533 (Online)

Publisher and founder: Yuzhnoye State Design Office, EDRPOU code 14308304.

Publication DOI: 10.33136/stma

Publication languages: Ukrainian, English.

Periodicity: twice a year.
In 2023-2024, taking into account the announcement of martial law in Ukraine, the Collection was issued once a year.
In 2025, the editorial and publication process was stabilized, and the Collection resumed publication every six months.

State registration of the printed media in the National Council of Ukraine on Television and Radio Broadcasting: media identifier – R30-01817 of 04.12.2023.